historical consequences of stmd funding shortfallsfebruary 2014 and completed march 2015) –...

Historical Consequences of

STMD Funding Shortfalls

James ReutherDeputy Associate Administrator for Programs

NASA Space Technology Mission Directorate

July 28, 2015

1

SEP DEMONSTRATION

MISSION

Solar Electric Propulsion (SEP) is an essential capability for current Human Mars mission planning – to efficiently move large payloads to Mars

SEP has numerous other crosscutting applications

Communications Satellites and Government Missions - more efficient orbit transfer- increased maneuvering flexibility- affordable power increase for communications or other payloads

Science and Exploration- observatory placement and station keeping- reaching distant destinations at less cost- higher power for communications or other payloads- transportation for cis-lunar, Mars, asteroid exploration

Satellite Servicing and Refueling

Space Tug between LEO, GEO or other Orbits - single use or reusable- multiple orbits and plane changes

Space Resource Access and Utilization

Orbital Debris Mitigation

Planetary Defense

4

Crosscutting Solar Electric Propulsion Development and Demonstration Objectives

• Successful transition of matured and tested Game Changing technologies to flight demonstration project

• Develop and demonstrate 25kW to 50kW class Solar Electric Propulsion System

• Extendable to 300kW for deep space human exploration

• Directly applicable to Science Mission Directorate and missions for Other Government Agencies

• A first demonstration mission targeted for the Asteroid Redirect Robotic Mission

• Develop & demonstrate Solar Electric Propulsion component technologies with commercial benefit

• Reduced mass, efficient packaging, deployable solar arrays for improved commercial satellite affordability and potential ISS retrofitting

• High power Hall thrusters for all electric commercial satellites

STMD Investments in SEP

Thrusters

Power Processing Units

• Developed and tested high power Hall thruster 12.5 kW-class (2X current SOA)

• Magnetically shielded design to provide long life

Solar Arrays

Designed, built and tested 25-kw-class advanced deployable Solar Array wings• MegaFlex “fold out” array (ATK)• Mega-ROSA “roll out” array (DSS)

Hall Effect Rocket with Magnetic Shielding (HERMeS)

Hall Thruster & Power Processing Unit (PPU) Development and Risk Mitigation

• Two 12.5 kW Hall Thruster Technology

Development Units

– Validated design methodology & tools

– Reduced mission and flight hardware

development risks

• 2 Brassboard PPUs

– 300Vin/800Vout (MFR reference)

– 120Vin/800Vout (Post-MCR reference)

Demonstrated full, integrated performance compatibility of 120-V and 300-V PPUs

with 12.5-kW Hall Effect Thruster

Post-test BN discharge chamber shows carbon deposition consistent with magnetically shielded operation

Pre-Test BN Post-Test

6

Technology Demonstration Missions

Asteroid Redirect Mission (ARM)combining Technology Demonstration, Exploration and Science objectives

Mission Concept • 40 kW-class SEP propels spacecraft to asteroid and

returns material to Lunar Distant Retrograde Orbit• Two 25 kW-class solar array wings and four 12.5-

kW electric Hall thrusters • Launch Date for Planning: December 2020• Launch Vehicle: Delta IV or SLS

Alternate and Complimentary Demonstrations• Functional space demonstration of large, advanced solar array on ISS

• RFI for this approach issued in December 2014

• Commercial or OGA partnership on a modified all-electric bus with significant orbital maneuvering capability

• Possible SMD partnership in multiple first-use high-powered SEP demonstrations including: cis-lunar, asteroid, and planetary missions

• Mars exploration precursors or demonstrations

8

Budgetary Challenges in Conducting a Comprehensive Large-Scale Demonstration

• Government-estimated SEP Module cost ($433M) significantly exceeds STMD in-guide budget profile ($229M)

• ARRM Budget Lifecycle and phasing presents significant challenges to timely perform mission. Launch initially June 2019, slipped to Dec. 2020.

• STMD in-guide covers: All SEP activities in FY15-16, all Ion Propulsion activities FY15-21, civil servant-only SEP mission design/studies FY15-21

• STMD in-guide gaps: SEP DDT&E - Power, Structures/mechanisms, Thermal, SE&I, RCS

• Part of Power gap includes SEP Power Solar Array contract, not funded beyond FY16 (STMD funds are short $40M)

• In general, cost estimates from BAA studies indicate:• A 40 to 50 kW-class SEP demonstration requires approximately $400M

• A 30 kW-class SEP demonstration requires approximately $250M

• If less funding is available in the STMD budget, a major cost-sharing partnership is required to accomplish a demonstration of this scale.

• Continued lack of full funding for STMD and indecision on fully funding ARRM has delayed progress towards a high powered SEP demonstration

STMD SOLAR ARRAY

DEVELOPMENT

Need for Solar Electric

Propulsion

• Future exploration missions require high power

Solar Electric Propulsion (SEP) to move cargo

and humans beyond Low Earth Orbit

• SEP is more efficient than chemical propulsion– SEP uses less fuel to the same destination reducing launch

mass/cost (20% - 50% reduction)

• STMD initiated a Solar Array Project in FY2011

as the first step towards complete capability– Initial vision was a flight demonstration of entire SEP concept, but

budget realities necessitated an array development project

– Autonomously deployed large area arrays were identified as “long

pole” in achieving goal

– Project targeted development metrics of total power (1.5x SOA)

and specific power (1.7x SOA)

– Two contracts were awarded (ATK & DSS) for a total project

budget of ~$11M

– Both ATK & DSS successfully deployed solar arrays under thermal

vacuum conditions (TRL 5)

– Analytically demonstrated extensibility to 250 kW-class systems

DSS: Mega-ROSA

ATK: Megaflex

Technology has significant end-user interest &

commercialization potential

Impact of STMD’s Solar Array

Investment

• Enables NASA’s future exploration missions

– Results in the fewest SLS launches & the least amount

of payload that must be launched to orbit for multiple

human exploration missions

• Enables development of satellite servicing system

• Empowers US commercial satellite industry with

larger & more capable systems

• Technology is being considered by every

domestic prime contractor as an affordable &

high-performance replacement to SOA arrays

– Space Systems Loral developing array with DSS for

commercial satellites

– Two proposers baselined DSS ROSA array for

Discovery mission proposals

– USAF funding ISS demonstration of small-scale ROSA

• Under consideration as an upgrade for ISS solar

power system

For internal NASA use only

July 2015 BPR

LASER COMMUNICATIONS

RELAY DEMONSTRATION

Enclosure Rear View illustrates layout,

structural, thermal maturity

Laser Communications Relay Demonstration

• Demo Description:

– A minimum two year flight demonstration to advance optical communications technology toward infusion into Deep Space and Near Earth operational systems, while growing the capabilities of industry sources.

• Objectives:

– Demonstrate bidirectional optical communications between geosynchronous Earth orbit (GEO) and Earth

– Measure and characterize the system performance over a variety of conditions

– Develop operational procedures and assess applicability for future missions

– Transfer laser communication technology to industry for future missions

– Provide an on orbit capability for test and demonstration of standards for optical relay communications

• Anticipated Benefits:

– A reliable, capable, & cost effective optical communication technology for infusion into future operational systems

• Anticipated NASA Mission Use:

– Next Generation TDRS, Deep Space and Near Earth Science

– ISS and Human SpaceFlight

• Attractive partnering arrangement with Space Systems/Loral as a hosted payload on a commercial telecom satellite and DoD partner for encryption.

LCRD is a hosted payload on an SSL

commercial telecom satellite

Payload Enclosure mounted on Earth Deck of typical SSL telecom satellite

LCRD KDP-A

• KDP-A held December 2012

• Project de-scoped before KDP-A

– On-Board Data Processing (Decoding, De-Interleaving, etc.), Store and Forward, DTN, DataProcessing and DTN at Both Ground Stations

– Networking Management

– In-Band Commanding and No Telemetry on theOptical Downlink

– Photon Counting Detector in Ground Station 2

– Commercialization of the Photon Counting Detector

– Delays GS2 delivery decision until end of FY13

• Notional Launch Readiness Date changed fromDecember 2016 (from proposal) to December2017 at KDP-A

• KDP-A LCC approved at $238.9M

• No change in LCC at KDP-B (May 2013), howeveradditional funding was approved for PPM work,upping LCC to $239.2M (October 2013)

KDP-A/B architecture - LCRD on SSL commercial telecom satellite, with 2 ground

stations (GS-1 at OCTL and GS-2 at White Sands)

Current Effort After Post KDP-B Re-Plan

• In addition to the de-scopes taken prior to KDP-A, LCRD was directed to take additional de-scopes and other changes during the re-plan activity (directed February 2014 and completed March 2015)

– Content removed/de-scoped from LCRD Budget:

• JPL Ground Station 1 starting in FY15 – Moved to SCaN Optical Ground Station Extension (OGS-X), five years of operation (two years base plus three years extended operations)

• De-scoped White Sands GS-2

• Deviation approved for EVM

• De-scoped E&PO

• Payload I&T moved from GSFC to SSL after Electrical/Optic Integration Test Bed

• Post launch checkout Science/Technology, Mission Ops, and LMOC Sustaining moved to SCaN OGS-X post checkout (L+60 days)

– Encryption scope added October 2014 (no waiver for encryption requirements), to be funded through SCaNand tracked separately

• Re-plan budgets were constrained by STMD funding levels for FY15 and FY16, with LCC at $294.5M, including encryption

• Notional Launch Readiness Date slipped to June 2019155/22/15 TDM MM Monthly Assessment

2016 2017 2018 2019

ProposalDec 2016

KDP-ADec 2017

Re-PlanJune 2019

2012 2013 2014 2015

LCRD Notional Launch Readiness Date Change

KDP-A$238.9M

KDP-B$238.9M

Re-Plan$294.5

LCRD LCC

DEEP SPACE OPTICAL

COMMUNICATIONS

DSOC STMD/GCDP Funding History

Introduction

• STMD/GCDP has been funding DSOC since the end of FY11 Original scope to mature key technologies (listed below) to TRL-5 by EO FY14

Isolation Pointing Assembly (IPA) Allows “dim-beacon” assisted low-bandwidth control for sub-micro-radian laser pointing accuracy

Photon Counting Camera Combines “dim-beacon” acquisition tracking and data uplink functions

Laser Transmitter assembly High peak-to-average power ratio and electrical-to-optical conversion for photon-efficient communication

Deep-space Optical Transceiver Integrates IPA and PCC with electronics for functional Flight Laser Transceiver (FLT)

Ground Receiver Detector Array Single photon counting arrays for detecting faint signal from deep-space using large area collectors

• Funding reduction in March 2013 De-scoped DSOC Project

Three out of five technology elements pursued Isolation Pointing Assembly

Photon Counting Camera

Ground Receiver Detector Array

Technology maturation to TRL-3/4 by EO FY14 instead of originally planned TRL-5

• Re-Scoped DSOC at Feb-March 2014 MOU between STMD/GCDP, HEOMD/SCaN, SMD/Discovery to fund DSOC through FY17

Mature integrated FLT to TRL-6

Ready for infusion into Discovery Mission to launch by Dec 2021

July 21, 2015

July 21, 2015


Funding Profiles

• Original Plan FY11-FY14

TRL-5 maturation Isolation Pointing Assembly (IPA)

Photon Counting Camera (PCC)

Laser transmitter Assembly (LTA)

Optical transceiver

Ground Detector Array

• De-scoped Plan FY11-FY14 TRL-3/4 Maturation

Isolation Pointing Assembly

Photon Counting Camera

Ground Detector Array

0

5000

10000

15000

20000

25000

30000

35000

FY11 FY12 FY13 FY14 FY15 FY16 FY17

Original Plan

Cum Original Plan

De-Scoped Plan

Cum De-scoped Plan

• Actual Funding FY11-FY15 and FY16-FY17 plan Mature TRL-6 Flight Laser Transceiver and Ground

Detector Array for 5m ground telescope

Ready to support Discovery Mission

IPA, PCC and LTA development benefitted from

SBIR funding

0

5000

10000

15000

20000

25000

30000

35000


Actual Funding

Cum Actual Funding

July 21, 2015


Summary

• How did shortage of funds early on keep DSOC from doing things in a full and timely

manner

Early development and risk areas could not be fully addressed Understanding why the WSi detectors work (to help design better detector4s with higher yield)

Developing larger than 32 x 32 flight detector arrays for DSOC

More efficient 1550 nm laser transmitter (as in resonantly pumped)

Other effects Loss of focus resulted in loss of some key personnel

Originally planned involvement of LL-MIIT and NASA/GSFC was de-scoped

Stretching of DSOC Project schedule with identification of Discovery Mission as a potential host

for Flight Transceiver has Benefitted DSOC Project from developments elsewhere, such as

IPA technology from Control Dynamics under SBIR

Provided opportunity for advancing engineering development not included in original scope

Flight Electronics

Thermal design

Harnessing and umbilical development

• STMD/GCDP, HEOMD/SCaN and SMD funding

distribution since MOU is shown in bar chart

0

1000

2000

3000

4000

5000

6000

7000


STMD/GCDP

HEOMD/SCaN

SMD


July 2015 BPR

INTEGRATED PHOTONICS

SMALL SPACECRAFT

DEMONSTRATION

Proposed STMD/SCaN

Integrated Photonics Initiative Now Under Threat

1 cm

US Industry has commercialized “Integrated photonics” to allow many electro-optical components, even glass fibers, to be “squeezed down”…..

…into the opticalequivalent of a micro-electronics “integrated circuit”

For NASA, this means that optical systems for communications and sensors can be reduced in size, mass, and cost by >> 100x by leveraging this commercially-available technology (some customization may be required)

STMD and HEOMD/SCaN are working to fund a cubesat flight demo of integrated photonics in FY17 ($8M total), which is now under threat due to funding reductions to STMD…

COTS Laser Comm Modem

..Based on Integrated Photonics

TRL 6 for LEO use only

Contains Proprietary Information – Do Not Distribute

Low-Cost Laser Comm Links Enabled by Integrated

Photonics now Threatened by STMD Funding

Reductions

Currently Funded: Laser Communications Relay Demonstration (LCRD) in GEO

With 2 “Traditional” Modems at 2.88 Gbps

Low Cost, Low SWaP Terminal for LEO Users to LCRD: Now Threatened

1000 km linksb/w 44 smallsats

Proposed SCaN/STMD Demonstration of Low-Cost Direct-to-Earth

100 Gbps Laser Terminal on Small-SatNow Threatened

Commercial Interest:High-Rate, High-Availability

LEO/MEO 100 Gbps DataNetwork Constellation

23

National Aeronautics andSpace Administration

CPST → eCryoEVOLVABLE CRYOGENICS – GRC

WAS:FLIGHT DEMONSTRATION OF CRYOGENIC PROPELLANT STORAGE AND TRANSFER TECHNOLOGIES THEREBY ADVANCING

CAPABILITIES FOR DEEP SPACE TRAVEL TO SERVE BOTH NASA EXPLORATION SYSTEMS AND COMMERCIAL LAUNCH

PROVIDERS

IS:PORTFOLIO OF GROUND DEMOS TO VALIDATE CRYOGENIC FLUID TECHNOLOGIES APPLICABLE TO SLS AND OTHER

EXPLORATION MISSIONS BEYOND LEO

Present Challenges for In-Space Cryogenic Systems

• We have no demonstrated capability to store cryogenic propellants inspace for more than a few hours

– SOA is Centaur’s 9 hours with boil-off rates on the order of 30% per day

• We have no demonstrated, flight-proven method to gauge cryogenicpropellant quantities accurately in microgravity

– Need to prove methods for use with both settled and unsettled propellants

• We have no proven way to guarantee we can get gas-free liquidcryogens out of a tank in microgravity

– Gas-free liquid is required for safe operation of a cryo propulsion system

– Need robust surface-tension liquid acquisition device (LAD)analogous to those in SOA storable propulsion systems

– Only known experience in the world is the single flight of the Russian Buransingle flight (liquid oxygen reaction control system)

• We have no demonstrated ability to move cryogenic liquids from onetank (or vehicle) to another in space

24

Centaur

Buran

NoteA flight demonstration with cryogenic propellant storage, expulsion,

and transfer can remedy these problems (and other more subtle ones)!

CPST Flight Demonstration

25

• CPST will:

– Demonstrate long-duration storage

– Demonstrate in-space transfer

– Demonstrate in-space, accurate gauging

CPST was baselined and approved for Phase B on Dec. 9, 2013

26

CPST VS. ECRYO

CPST• Flight Demonstration utilizing SpaceX Dragon Trunk

• Technologies evolve from TRL 5 to 7

• Payload size: 224 kg LH2 (vs. 20 kg), 1.5 m diameter tank (vs. .3m diameter)

• Mission Duration: 1-2 months (vs. hours)

• Technologies Demonstrated on 1.5m tank:• Passive thermal control• 2 transfers using screen channel liquid

acquisition devices • RFMG

• Technologies Developed:• High Accuracy Delta P Transducer• Valve Seat Leak Test

• Implementation• In-house payload build• Delivery Order on existing CRS Contract for the

LV, S/C Bus, Mission Operations, and I&T

• Deliverables: • Micro-gravity data to anchor CFM models, • Industry workshops to share data, • Conference presentations

eCryo• Ground Demonstration of a CFM technology portfolio

• Technologies develop to a range from 3 to 6

• Ground Tank size: 4m diameter

• N/A.• Technologies Demonstrated:

• SHIIVER passive thermal control on 4m tank (MLI and Vapor Cooling)

• RFMG on GSFC RRM3 Mission yielding flight data

• Technologies Developed:• High Accuracy Delta P Transducer• Valve Seat Leak Test• Super Insulation• IVF for SLS

• Implementation• In-house research and development

• Deliverables: • Industry workshops to share data, • Conference presentations, • Ground data to anchor CFM models

27

ECRYO – EVOLVABLE CRYOGENICS

• eCryo will:

– Develop technology for extended in-space missions with near term gains geared toward industry.

– Increase capabilities of analysis tools for predictive simulations of in-space cryogenic systems.

Structural Heat Intercept Insulation Vibration

Evaluation Rig (SHIIVER)

Radio Frequency Mass Gauge (RFMG) for Robotics Refueling Mission 3 (RRM3)

CFM Analysis

Space Launch Systems (SLS)

Stages support

eCryo Portfolio Products

eCryo was baselined and approved for Phase C on Apr. 30, 2015

EDL ARCHITECTURE

DEVELOPMENT

Need for Advanced EDL

Architectures

• Mars’ atmosphere results in significant

EDL challenges– Atmosphere causes vehicle to slow down

– Atmosphere is dense enough to require a heat

shield

– Atmosphere is not dense enough to provide

substantial drag necessitating large surface area

heat shields

• State of the Art EDL architectures are

not sufficient for future human

exploration missions to Mars– Rigid aeroshells are constrained by launch

shroud geometry

– Current EDL technologies/approaches (MSL,

Mars 2020, etc…) are limited to 1 mt payload

mass to Mars’ surface

– Human exploration requires landed mass in

excess of 18 mtMars Science Laboratory (MSL) Entry,

Descent, and Landing Architecture

STMD’s Advanced EDL

Investments

• STMD has initiated investments, and

developed extensive expertise, in two

deployable EDL architectures for human

missions to Mars

– Hypersonic Inflatable Aerodynamic Decelerator

(HIAD): Inflatable tori with overlaid, flexible TPS

– Adaptable Deployable Entry and Placement

Technology (ADEPT): Mechanically deployed

structure with carbon fabric TPS

• Both entry systems are folded for launch

and deployed prior to Mars entry

– Provide rigid aerodynamic surface and thermal

protection for hypersonic deceleration at scales in

excess of 25 meters

– HIAD & ADEPT can also be used for robotic

exploration at diameters between 6 and 10 meters

Hypersonic Inflatable Aerodynamic

Decelerator (HIAD)

Adaptable Deployable Entry and

Placement (ADEPT)

HIAD & ADEPT Opportunities

& Accomplishments

• Significant progress has been made

maturing HIAD & ADEPT over the past

decade– HIAD successfully completed a 3 meter diameter flight

test (IRVE-3 in 2012) & 6 meter wind tunnel test

– ADEPT successfully completed a 0.7 meter diameter

wind tunnel test campaign and fabrication of 2 meter

diameter ground test article

ADEPT ground test article (2m dia.)

HIAD architecture “cut-

away” (top) and IRVE-3

sounding rocket flight

d

• Both EDL development activities have

been impacted by budget reductions– Potential HIAD development activity:

• Execution of 3.7 meter diameter, high energy reentry

flight test in partnership with ULA (asset recovery

demonstration)

• Ground-based maturation effort to improve aeroshell

capabilities including scale up to >10 meter diameter

– Potential ADEPT development activity:

• Execution of six meter diameter ground test program

• One meter diameter ADEPT test article sounding

rocket flight test

emonstration (right)

POWER GENERATION &

STORAGE DEVELOPMENT

Power Generation & Energy Storage

Major NASA Power Capability Needs:Mars Stationary Surface Power

– In order to live on Mars (or Lunar Surface) power generation is required under all scenarios, present goal is 40kW continuous power; technology baseline for capability satisfaction is nuclear fission, however solar power is possible

Mars Mobile Surface Power

– In order to explore planetary surface; rovers are required technology baseline is 5-10kw fuel cell, however batteries are possible

In-Space Propulsion for Mars Cargo

– Present Mars planning includes 400kw solar arrays for SEP propulsion system; Nuclear Thermal System is under consideration but not likely

Robotic Interplanetary Missions

– Beyond Jupiter, solar power is not viable, present Radio-Isotope Power Systems suffer from limited efficiency and the required use of PU-238; improvements to technology required to sustain Planetary Science Mission Capability

Major Power and Energy Technology Enhancements:– Batteries with higher energy density required across multiple missions, result in reduced

mass

– Radiation tolerant solar cells impact End of Life efficiency of solar arrays (mass) across all missions

– Radiation tolerant, along with high temperature/voltage, electronic components

– Wireless energy transfer allows dislocation of power generation and need across multiple missions

STMD Power & Energy Portfolio

High Energy Density Batteries:

– NASA has a need for batteries with higher energy density (>300wh/kg @ cell level) than State of the Art Li+ technology can provide

– In FY14 STMD initiated a collaboration with ARPA E on advanced battery system. Project is beginning second year and hopes to deliver battery system for Adv. EVA Suit in 2017 (~$5M spent over 4 years)

Fuel Cell Systems:

– NASA spacecraft and surface systems require fuel cells to generate power over intermediate time horizons and in conjunction with other energy sources, e.g. solar cells

– STMD took over an existing PEM Fuel Cell project when the Mission Directorate was established in 2011, delivered 1kw and 3 kw test articles to HEOMD/AES for testing on rovers (~$8M spent over 4 years); without pressing need STMD was forced to curtail work in FY14 and eliminate funding in FY15

Photovoltaics:

– Major photovoltaic effort in STMD has been Solar Array Systems project

– NASA has unique needs for Low Intensity, High Temperature, and High Radiation Tolerant solar cells however budget has limited ability to pursue research in this area

Nuclear Systems:

– STMD Kilopower project is pursuing a 1kW fission system using U235 vs Pu238 (~$14M over 4 years), demonstration planned for 2018

– System will be extensible to 10kW x4 system capable of being used for Mars surface power requirement

– If successful system may also be used for Interplanetary Robotic Missions in the future

Power Beaming:

– STMD recently released an RFP for which Wireless Power Transfer was a topic for consideration

1 Kw Kilopower Fission System

DEEP SPACE ATOMIC CLOCK

DEMONSTRATION MISSION

DSAC Quad Chart

Objective: Develop an advanced prototype mercury-ion atomic clock (TRL 7) and demonstrate for a year in space, providing the unprecedented performance needed for the next generation of deep space navigation and radio science. Identify steps to build a more power efficient and smaller infusible version.

Benefits to Space Navigation and ScienceEnable shift to a more flexible/extensible 1-Way radionavigation architecture from the current 2-Way model• Enables usable multiple spacecraft per aperture tracking • Enables use of 1-Way uplink X-band tracking/open loop recording for

robust gravity science solutionsFundamental to autonomous radio navigation• Contributes to smaller landing errors and to mass efficient pinpoint

landing via propellant savings• Needed for fully autonomous aerobraking operationsIncrease navigation & radio science tracking data accuracy by 10 times and quantity by 2 times• Improves Mars orbit determination to < 1 m with Ka band trackingPotential to improve clock performance of the next GPS system by 50 x

Key Features for reliable in-space use• No lasers, cryogenics, or other consumables → long life• Existing vacuum technology and no microwave cavities → easier

manufacturability• Radiation tolerant at levels similar to GPS Rb Clocks

Multi-pole TrapMulti-pole Trap

Quadrupole TrapQuadrupole Trap

Titanium Vacuum Tube

Titanium Vacuum Tube

Technology highlights• State selection via UV optical pumping using Hg ions• Extreme stability via no wall collisions & high-Q microwave line • Multi-pole trap yields insensitivity to disturbances

State‐Of‐Art USO

DSAC (Demo)

GPS IIF Rb (w/ dri )

GPS Cs

Galileo H‐maser

ACES H‐Maser

GLONASS Cs

NASA/SAO H‐Maser

ACES Cold Cs (in lab)

ACES Cold Cs (goal)

DSAC (2nd Gen)

GPS IIF Rb (w/o dri )

0.001

0.01

0.1

1

10

100

1000

0 10 20 30 40 50 60 70 80 90 100

Accumulated

Ran

ge Error

@ 1

Day

(m)

Mass (kg)

Legend Flown Not Flown (yet)

Deep Space 2‐Way Range Precision ( 1m)

DSAC LCC and Schedule History

Date EventPlanned Launch

LCC Total $M

HEOMD Share $M

SMD Share $M

Notes

9/15/2011Original JPL TA

Mar 2015 59 15 0

3/7/2012 KDP B Mar 2015 59 15 0Access to Irridium

Space TBD after termination with

11/6/2013 KDP C Sept 2015 67 19 0Guideline error ($1M), (4mo. Slip, $2.3M)

Host Change to Surrey

7/15/2015 KDP D Sept 2016 73 21 4GS costs ($0.4M), missed ONC ($0.8M), and launch slips ($0.8M) and overruns ($4M)

• 9 % cost growth from KDP C baseline, due to technical issues with the clock and external events. DSAC project has managed to cost very well to date.

• Projec t on track to deliver demonstration unit/flight payload to Surrey host in December, following final environmental test sequence and final characterization.

• Custome r support increasing as project has had successful implementation– Increase d (HEOMD/SCAN) and new (SMD/PSD) cost sharing– Interest expressed in obtaining project ground assets when available (SMD)– Increase d interest in mission and any non‐recurring engineering necessary for

infusion into Class B mission• DSA C accommodation study with Europa Clipper Pre‐project began in June• DSA C briefed SMD PSD management on the current DSAC mission and

development of a future DSAC for Clipper in July

Schedule Alignment with Europa

Now

S/C AIT

Complete Mar ‘16

Implementation

Risks Retired

TRL 6 TRL 7DSAC ScheduleFY12 FY13 FY14 FY15 FY16 FY17 FY18

Phases

DSAC Project Milestones

A C EDB

SRR PDR CDR/SIR PSR FRR LRR

Launch

DSAC accommodation

study with the Europa

Clipper pre-project

began in June.

Europa ScheduleSRR/MDR PDR

DSAC is phased in advance of Europa, offering low implementation risk

Infusion Story

PDR

Launch

PDR

Launch

Launch

PDR

LaunchPDR

Launch

LaunchPDR

LaunchPDR

$

$

NASA-funded

20+ Years of Prior

Hg Ion Atomic

Clock Research

Europa Project

Funded Infusion

Activity

1990

First Flight (TRL 7)

NASA DSAC

2012

JPL Funded

“Team-A”

Mission

Concept

Development

Some Discovery

‘14

Interested Parties,

Outcome

Unknown

2014

Infusion Window

Launch

AFRL MAFS

PDR

AFRL NavSat

Europa Clipper – Plan Based on Current Funding

Discovery or NF Missions

2016

GPS III SV 9+

MIL-SATCOM “5x” Constellation

NRO Potential Missions

Mars Orbiter (Next Opportunity)

2018 2020 2022 2024

GREEN PROPELLANT

INFUSION MISSION

Green Propellant Infusion Mission (GPIM) Project Performance

July 2015 BPR

Technical / Test Performance:

• GPIM will demonstrate the on-orbit use of the HAN-based green monopropellant AF-M315E as an alternative to hydrazine for attitude control and orbit change

• Green Propellant Propulsion Subsystem (GPPS) I&T is nearing completion

– Decision was made by STMD on 4/17 to use an all 1N thruster flight configuration, removing schedule and programmatic risk of 22N thruster from mission

– All five 1N thrusters were manufactured and successfully completed their acceptance test sequence (functional testing, hot-fire, vibration testing and post vibration functional tests). This activity began in April and was completed in June.

– All thrusters have been installed, electrically integrated, and successfully welded in the system

– Fracture mechanics testing for the propellant tank completed

– System testing planned for week of July 20

– GPPS delivery from Aerojet to Ball planned for August 2015


All 5 1N thrustersWelded

GPPS Propulsion Deck (top)

GPPS Propulsion

Deck (bottom)

GPPS integration complete


July 2015 BPR

Green Propellant Infusion Mission (GPIM) Challenges

Primary Challenges

• Much higher flame temperature and lower known allowable soak-back temperature made design of AF-M315E thrusters more challenging vs. conventional N2H4 thrusters

How it manifested itself:

• Flight-weight thruster design required refractory metals – leading to process development schedule delays, dissimilar material welding/brazing issues, significant catalyst bed heater development

• Detailed refractory materials properties at thruster operating temperatures not available – 22N thruster low cycle fatigue issues discovered in life test

AllowableSoak-backTemperature

N2H4: 150 ºCAF-M315E: 90 ºC Flame Temperature N2H4: 900 ºC

AF-M315E: 1800 ºC

Preheat Temperature N2H4: 120 ºCAF-M315E: 350 ºC

Green Propellant Infusion Mission (GPIM) Challenges

July 2015 BPR

Technology Challenges Have Driven Cost


• Aerojet was able to maintain schedule until life testing began

• Schedule delays driven by manufacturing readiness (immaturity of design going into CDR) delayed test readiness 5 months

• Test issues on 22N thruster caused another 3-4 months of delay

• Nine months of additional thruster development/testing has accounted for 70% of cost growth

• Launch vehicle-driven schedule delay has driven 20% of cost growth

Strategic Technology Readiness Assessment is Important

• Detailed assessment of readiness prior to committing to a flight schedule is vital

• Assessment needs to take into account not only the maturity level of the critical technologies, but also the readiness to integrate into flight hardware

historical consequences of stmd funding shortfallsfebruary 2014 and completed march 2015) –...

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